Airbus Operations Sl

Airbus Operations Gmbh

Enrique Vera Villares

Jose Maria Pina Lopez

Javier Cabeza Huertas

Elena Arévalo Rodríguez

Diego Folch Cortés

José María Pina López

Maria Aranzazu Garcia Patino

José Maria Pina López

Melania Sánchez Pérez

Elena Arévalo Rödríguez

María Pilar Muñoz López

José María Pina Lopez

Ignacio Jorge Outon Hernandez

Loreto Martínez Fernández

José María Pina LÓPEZ

Javier Cabeza Huerta

Jose María Pina LÓPEZ

Oscar De La Cruz GARCÍA

Antonio De JULIÁN Aguado

A lower fuselage shell for an aircraft rear fuselage section, wherein the lower fuselage shell is made of a composite material and comprises at least one lower skin and stringers integrally formed with the lower skin, and frame segments extending crosswise relative to the stringers. Shear-ties are co-cured or co-bonded with the lower skin and extend crosswise relative to the stringers. Frame segments are fastened to the shear-ties, such that the frame segments are distanced from the lower skin. An aircraft rear fuselage section comprises an upper fuselage shell and the described lower fuselage shell. The upper fuselage shell has an upper skin reinforced with omega-shaped stringers, and the lower shell has a lower skin reinforced with T-shaped stringers.

Aircraft rear fuselage section and manufacturing method thereof

The method comprises the manufacture of a front section () and an rear section () with an assembly structure integrated into the rear section and the subsequent assembly of the two sections. The manufacture of the front section () comprises the manufacture of a main portion () of the front section separated from a coupling portion () of the front section. The assembly of the two sections comprises the assembly of the main portion () with the group comprising of the rear section assembly () and the coupling portion () of front section.

Method for assembling fuselage sections of an aircraft

Composite aircraft frame () comprising two segments (), each of these segments () being single unitary element made in composite material and comprising at least one web (), a stiffening structure and a fitting (), the two segments () being joint by the fittings () using rivets, forming the aircraft frame (). The invention also refers to a method for fabricating such an aircraft frame ().

Composite aircraft frame

Weathertight fitting () for the mounting of the tail vertical stabilizer of an aircraft in a rear area of its fuselage, the construction being based on a casing () made with a composite material as one unitary piece and some frames () that are comprised of: one first piece () comprised of two bodies ('), that include the mounting lugs (&#x2032;) for the tail vertical stabilizer and some vertical walls (&#x2032;) for joining the fitting () to the frames () of the fuselage, and a weathertight central profile (); two pairs of additional pieces (&#x2032;) of angular shape, that include some horizontal walls (&#x2032;) for joining to the casing () and some vertical walls (&#x2032;) for joining to the aforementioned bodies (&#x2032;). All the weathertight fitting's () pieces are made with a composite material.

Weathertight fitting for aircraft tail vertical stabiliser mounting

A method for repairing the skin of the fuselage of an airplane from the inside to be used when the skin of the fuselage has been damaged between a first stringer and a second stringer adjacent to the first one is provided. The method includes filling the damage, placing a first doubler over the filling, placing a second doubler over the first doubler and bending this second doubler at least over a flange of one of the stringers, and securing the second doubler.

Inner bent repairment

A ball-joint support for thin parts, through which a ball-joint is operably coupled to a thin part, and where the ball-joint includes an inner part with a central coaxial orifice through which a longitudinal axis is introduced, and an outer part that engages complementarily to the inner part is provided. The ball joint support includes a cap including a central through hole in which the ball joint is embedded inside via the outer part, and externally, the cap is embedded in a cylindrical opening included in the thin part, and mechanical means for axial retention of the thin part to the cap, wherein the thickness of the cap is greater than the thickness of the thin part where the cap engages.

Ball-joint support for thin parts

A joint construction for an aeronautical structure made from composite material having an internal structural element and an adjoining skin element which define the aeronautical structure, which includes a coupling element disposed between and contiguous with the internal structural element and the adjoining skin element, wherein the coupling element has opposing adjoining diagonally configured end portions which form a wedge shaped diagonal joint therebetween which terminates at the internal structural element at one end and the skin element at the other end, and a plurality of rivets extending from the internal structured element to the adjoining skin, across the coupling element and across the diagonal joint.

Arrangement of a circumferential joint of structural elements with a coupling element manufactured in composite material

A fitting is provided to fix a vertical tail stabilizer of an aircraft to a composite skin and a composite frame of the aircraft in an area of a rear fuselage thereof. The fitting includes a first composite piece having lugs to attach to the vertical tail stabilizer and having vertical walls to fix the fitting to the composite frame of the rear fuselage. The fitting further includes at least one pair of additional composite pieces, each having a horizontal wall to fix the fitting to the composite skin of the rear fuselage. A second pair of additional composite pieces may be provided to further secure the fitting to the skin of the aircraft.

Fittings for attaching the vertical tail stabilizer of an aircraft

A joint arrangement for composite-material structural members in components including a skin and a plurality of structural members, applicable to pairs of first and second intersecting structural members, such as a beam and a frame in an aircraft fuselage, both members having a configuration which includes webs, inner flanges and outer flanges, in which, in the zone of intersection between said members, the laminations of one or both flanges of the first member include transverse flaps which are joined to one or both flanges of the ends of the segments of the second member which are separated at the intersection, acting as means for transmission of loads between them.

Growing community of inventors

Madrid, Spain

Enrique Vera Villares